EP3006678B1 - Ring segment with cooling system and gas turbine - Google Patents
Ring segment with cooling system and gas turbine Download PDFInfo
- Publication number
- EP3006678B1 EP3006678B1 EP15188702.3A EP15188702A EP3006678B1 EP 3006678 B1 EP3006678 B1 EP 3006678B1 EP 15188702 A EP15188702 A EP 15188702A EP 3006678 B1 EP3006678 B1 EP 3006678B1
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- EP
- European Patent Office
- Prior art keywords
- cooling
- cooling passage
- ring segment
- segment
- end portion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000001816 cooling Methods 0.000 title claims description 395
- 238000011144 upstream manufacturing Methods 0.000 claims description 89
- 239000000567 combustion gas Substances 0.000 claims description 76
- 239000007789 gas Substances 0.000 claims description 30
- 239000011295 pitch Substances 0.000 description 16
- 230000000694 effects Effects 0.000 description 7
- 238000002955 isolation Methods 0.000 description 7
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 230000002093 peripheral effect Effects 0.000 description 4
- 230000003685 thermal hair damage Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000470 constituent Substances 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Definitions
- the present invention relates to ring segment with a cooling system of a gas turbine and to a gas turbine.
- combustion gas of a high temperature and high pressure passes through the turbine of a gas turbine, which is used in the generation of electrical energy, cooling of the ring segment and the like is important in order to continue stabilized operation.
- cooling of the ring segment and the like is important in order to continue stabilized operation.
- the temperature of combustion gas continues to increase.
- FIG. 11 is a cross-sectional view that shows the internal structure relating to the turbine of a gas turbine.
- the gas turbine supplies combustion gas FG generated in a combustor 3 to turbine vanes 7 and turbine blades 8, and by causing the turbine blades 8 to rotate a rotating shaft 5, converts rotational energy into electrical power.
- the turbine vanes 7 and the turbine blades 8 are alternately disposed from the upstream to the downstream of the flow direction of the combustion gas FG.
- a plurality of turbine blades 8 is disposed in the circumferential direction of the rotating shaft 5, and thus rotate together with the rotating shaft 5.
- the turbine vanes 7 are disposed on the upstream of the turbine blades 8 in the flow direction of the combustion gas FG, and a plurality are disposed in the circumferential direction of the rotating shaft 5, similarly to the turbine blades 8.
- a ring segment 60 is disposed annularly on the outer periphery side of the turbine blades 8, and between the ring segment 60 and the turbine blades 8, a tip clearance is provided in order to avoid mutual interference.
- FIG. 12 is a cross-sectional view of a conventional ring segment.
- the ring segment 60 is formed from a plurality of segment bodies 61, and is oriented annularly in the circumferential direction of the rotating shaft 5.
- Each segment body 61 is supported by a casing 67 via hooks 62 of the segment body 61 and an isolation ring 66.
- a collision plate 64 that is supported from the isolation ring 66 is equipped with a plurality of small holes 65.
- a plurality of cooling passages 63 are disposed in the axial direction of the rotating shaft 5.
- cooling air CA which is a portion of bleed air of a compressor is supplied to each segment body 61 of the ring segment 60 from a supply hole 68 of the casing 67.
- the cooling air CA after the impingement cooling jets into the combustion gas space from the downstream end of the segment body 61 in the flow direction of the combustion gas (in the direction from the left side to the right side on the sheet of FIG. 11 ) via the cooling passage 63 convection cooling of the segment body 61 is carried out by the cooling air CA that flows through the cooling passage 63.
- Patent Document 1 discloses a ring segment that is provided with the abovementioned collision plate. An example is illustrated in which when the cooling air that has performed impingement cooling is supplied to opening portions that are disposed in the outer circumferential surface of the ring segment (segment body) and discharged from the downstream end of the ring segment in the flow direction of the combustion gas FG to the combustion gas space via the cooling passage (cooling air holes), it cools the ring segment.
- Patent Document 2 discloses a structure that is an improvement on that disclosed in Patent Document 1.
- a cooling passage (first passage) that jets a portion of cooling air that has performed impingement cooling from the upstream end of the ring segment (segment body) in the flow direction of the combustion gas to the combustion gas space is disclosed, and a cooling passage (second passage) that jets a greater part of the remaining cooling air after the impingement cooling from the downstream end in the flow direction of the combustion gas to the combustion gas space is disclosed.
- first passage that jets a portion of cooling air that has performed impingement cooling from the upstream end of the ring segment (segment body) in the flow direction of the combustion gas to the combustion gas space
- second passage that jets a greater part of the remaining cooling air after the impingement cooling from the downstream end in the flow direction of the combustion gas to the combustion gas space is disclosed.
- Patent Document 1 there is a region in which a cooling passage is not disposed on the upstream end portion of the ring segment in the flow direction of the combustion gas, and so in the case of the combustion gas further increasing in temperature, the problem arises of the upstream end portion of the ring segment being damaged thermally out by the high temperature combustion gas.
- the present invention was achieved in view of the above problems, and has as its object to provide a cooling system of a ring segment that has as its object to prevent thermal damage of the ring segment as the combustion gas increases in temperature and improve the thermal efficiency by reducing the amount of cooling air, and a gas turbine.
- the present invention adopts a ring segment with a cooling system having the features of claim 1 to solve the aforementioned problem points.
- Preferred embodiments of the ring segment are defined in the dependent claims.
- the cooling system of ring segment of the present invention is a ring segment cooling system that is formed from a plurality of segment bodies that are arranged in the circumferential direction to form a ring shape, and that cools a ring segment of a gas turbine that is arranged in a casing so that the inner peripheral surface is kept a fixed distance from the tips of turbine blades, is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that is arranged in the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a combustion gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.
- the present invention provides the first cavity in the upstream end portion of the ring segment in the flow direction of the combustion gas, and since the cooling air of the cooling space is supplied to the first cavity via the first cooling passage, and furthermore discharged to the combustion gas space from the downstream end portion in the flow direction of the combustion gas via the second cooling passage, the length of the cooling passage is elongated, and the convection cooling of the upstream end portion of the segment body which has an intense heat load is enhanced. For that reason, thermal damage of the upstream end portion of the segment body by the high temperature combustion gas is avoided.
- the first cooling passage and the second cooling passage have a structure of turning back in the axial direction of the rotating shaft in the first cavity.
- the first cooling passage and the second cooling passage have a structure of turning back in the flow direction of the combustion gas in the first cavity, the entirety of the cooling passage with a long passage length is put in the main body of the segment body in a compact manner, and miniaturization of the ring segment is achieved.
- the first cooling passage and the second cooling passage each be arranged in a plurality in an annular shape with respect to the rotation direction of the rotating shaft, and be arranged so as to be mutually parallel in the radial direction.
- the first cooling passage and the second cooling passage are arranged so as to be mutually parallel, the distance between adjacent cooling passages is uniformly maintained, the temperature distribution of the upstream end portion diminishes, and the cooling performance of the upstream end portion of the segment body improves.
- the first cooling passage and the second cooling passage each be arranged in a plurality in an annular shape with respect to the rotation direction of the rotating shaft, and the first cooling passage be arranged sloping in the rotation direction of the rotating shaft with respect to the second cooling passage.
- the cooling air that is supplied to the first cavity via the first cooling passage jets toward the bottom surface of the first cavity, and performs impingement cooling of the bottom surface of the first cavity, it is effective for cooling of the upstream end portion of the segment body where the heat load is intense.
- the first cooling passage has a shorter length than the second cooling passage and be disposed further to the outer circumferential surface side of the main body than the second cooling passage.
- the fist cooling passage is arranged at the outer circumferential surface side of the upstream end portion, and the second cooling passage is arranged at the inner circumferential surface side of the upstream end portion, the outer circumferential surface side and the inner circumferential surface side of the upstream end portion of the segment body are cooled together, and the cooling performance of the upstream end portion of the segment body improves.
- the hole diameter of the second cooling passage be smaller than the hole diameter of the first cooling passage.
- the present invention since it is possible to maintain a high pressure in the first cavity, it is possible to increase the velocity of the cooling air that flows through the second cooling passage, and the cooling performance of the inner circumferential surface side of the segment body improves.
- the hole pitch of the second cooling passage in the rotation direction of the rotating shaft be smaller than the hole pitch of the first cooling passage in the rotation direction of the rotating shaft.
- the hole pitch of the second cooling passage in the rotation direction of the rotating shaft is smaller compared to the first cooling passage, the cooling effect of the second cooling passage is high, and the cooling performance of the segment body improves.
- a third cooling passage be arranged at the side end portion on the upstream of the segment body in the rotation direction of the rotating shaft, and that it communicate from the cooling space to the combustion gas space in the side end portion on the upstream of the segment body in the rotation direction of the rotating shaft.
- the convection cooling of the side end portion on the upstream of the segment body in the rotation direction of the rotating shaft is enhanced.
- a fourth cooling passage be arranged at the side end portion on the downstream of the segment body in the rotation direction of the rotating shaft, and that it communicate from the cooling space to the combustion gas space in the side end portion on the downstream of the segment body in the rotation direction of the rotating shaft.
- the fourth cooling passage since providing the fourth cooling passage cools the side end portions of both sides of the upstream and the downstream of the segment body in the rotation direction of the rotating shaft, the convection cooling of the segment body is enhanced.
- the third cooling passage or the fourth cooling passage communicate with the first cavity via the second cavity or the third cavity.
- the cooling performance of the third cooling passage or the fourth cooling passage in the vicinity of the upstream end portion is enhanced.
- a gas turbine of the present invention is preferably provided with the aforementioned cooling system of ring segment.
- the amount of cooling air of the gas turbine is reduced, and the thermal efficiency of the gas turbine improves.
- the cooling of the upstream end portion of the ring segment is enhanced, and thermal damage of the ring segment is avoided. Also, it is possible to provide a gas turbine that keeps down the amount used of cooling air to a minimum, and further increases the cooling efficiency and cooling performance of a ring segment. Accordingly, it is possible to improve the reliability and the operating efficiency of a gas turbine.
- FIGS. 1 to 7 and FIG. 11 A description of the first embodiment shall be given based on FIGS. 1 to 7 and FIG. 11 .
- FIG. 1 is an overall configuration diagram of the gas turbine.
- a gas turbine 1 has as main constituent elements a compressor 2 that compresses combustion air, a combustor 3 that injects fuel FL into the combustion air that is sent from the compressor 2, causes a combustion, and generates combustion gas, a turbine 4 that is positioned on the downstream of this combustor 3 and driven by the combustion gas that has left the combustor 3, a generator 6, and a rotating shaft 5 that integrally couples the compressor 2, the turbine 4, and the generator 6.
- FIG. 2 shows a cross section of the essential portions of the ring segment of the gas turbine.
- a ring segment 10 is a constituent member of the turbine 4 that is supported by the casing 67, and is constituted by a plurality of segment bodies 11 that are arranged in the circumferential direction of a rotating shaft 5 to form a ring shape.
- the segment bodies 11 are positioned so that a fixed clearance is secured between the inner peripheral surface 11a of the segment bodies and a tip 8a of a rotor blade 8.
- the ring segment 10 is formed for example from a heat-resistant nickel alloy or the like. Note that the reference numeral 7 in the drawing denotes turbine vanes of the turbine 4.
- the main constituent elements are a main body (bottom plate) 12, hooks 13, and a collision plate 14.
- the segment body 11 is attached to a isolation ring 28 via the hooks 13 that are provided on the upstream and downstream in the flow direction of the combustion gas FG, and is supported by the casing 67 via a isolation ring 28.
- the segment body 11 is provided with the main body 12, the collision plate 14, the hooks 13 that are arranged on the upstream and downstream in the flow direction of the combustion gas FG, and a cooling space (hereinbelow called a "cooling space") 29 that is enclosed by side end portions 18 an 19 (refer to FIG.
- the cooling space 29 is formed in the segment body 11, and is a space that is in contact with an outer circumferential surface 12a side of the main body 12 that is positioned on the rear surface (outer peripheral surface), viewing from the inner peripheral surface 11a of the segment body 11.
- the collision plate 14 is installed on the upper portion of the cooling space 29. A large number of the small holes 15 through which the cooling air CA for impingement cooling passes are bored in the collision plate 14. Above the collision plate 14, a reception space 30 is arranged in which cooling air CA in the casing 67 is introduced via a supply hole 68.
- the cooling air CA that is supplied to the reception space 30 jets from the small holes 15 in the state of the entirety being equalized to approximately the same pressure, and performs impingement cooling of the inner circumferential surface (outer circumferential surface 12a of the main body 12) of the cooling space 29.
- FIG. 3 is a perspective view of the segment body 11.
- the combustion gas FG flows in the direction from the left side to the right side on the sheet surface, and the rotation direction (rotation direction of the turbine blades) R of the rotating shaft 5 is a direction that is perpendicular to the axial direction of the rotating shaft.
- the segment body 11 is supported by the isolation ring 28 via the hooks 13.
- the collision plate 14 is fixed to inner walls 12b of the main body 12 of the segment body 11.
- the collision plate 14 has a shape in which the center portion 14a is indented in a concave shape from the periphery 14b. That is, since the main body 12 of the segment body 11 is placed in a higher temperature state than the collision plate 14, thermal elongation becomes larger than the collision plate 14 in the axial direction of the rotating shaft and the rotation direction R of the rotating shaft. For that reason, the collision plate 14 is pulled from the inner wall 12b side of the main body 12, and thermal stress occurs in the collision plate 14. However, by providing the indentation in a concave shape in the center portion 14a of the collision plate 14, the flexibility of the entire collision plate 14 increases, and so there is the effect of the thermal stress that is generated being eased.
- FIG. 4 is a plan view of the segment body viewed in the direction of the rotating shaft from the collision plate side of the segment body 11.
- a first cavity 20 is arranged in a direction approximately perpendicular to the axial direction of the rotating shaft 5.
- a cooling passage (first cooling passage) 21 that couples the cooling space 29 and the first cavity 20 is provided in the axial direction of the rotating shaft 5
- a cooling passage (second cooling passage) 22 that opens from the first cavity 20 to a downstream end portion 17 of the downstream in the flow direction of the combustion gas FG is arranged in the axial direction of the rotating shaft.
- the first cavity 20 plays the role of a manifold that mutually couples the first cooling passage 21 and the second cooling passage 22.
- FIG. 5 shows a cross section of the segment body shown in FIG. 4 (cross section along line A-A), and FIG. 6 shows a side view (cross section along line B-B).
- FIG. 7 shows a cross section of the segment body viewed from the axial direction of the rotating shaft 5 (cross section along line C-C).
- first cooling passage 21 and the second cooling passage 22 shall be described with reference to FIG. 4 to FIG. 7 .
- first cooling passage 21 and the second cooling passage 22 are both bored so as to pass through the cross section of the main body 12 of the segment body 11 in the axial direction of the rotating shaft 5.
- the first cooling passage 21 and the second cooling passage 22 are arranged in parallel at a regular interval so as to mutually form one row in the vertical direction (the diameter direction of the rotating shaft 5), in the cross-sectional view seen from the axial direction of the rotating shaft 5. Also, for both the first cooling passage 21 and the second cooling passage 22, a plurality of the cooling passages 21 and 22 are arranged in an annular shape at a predetermined hole pitch with respect to the rotation direction R of the rotating shaft 5.
- the first cooling passage 21 and the second cooling passage 22 are arranged so as to overlap in two rows in the vertical direction from the side end portion 18 on the upstream in the rotation direction R of the segment body 11 to the side end portion 19 on the downstream. Also, as for the first cooling passage 21 and the second cooling passage 22, adjacent cooling passages are arranged at a predetermined hole pitch so as to be mutually parallel in the rotation direction R of the rotating shaft 5. Furthermore, the first cooling passage 21 and the second cooling passage 22 are arranged so as to be mutually parallel in the axial direction of the rotating shaft 5.
- the cooling passage that is arranged in the axial direction of the rotating shaft 5 (second cooling passage 22) is provided along the inner circumferential surface 11a of the segment body 11, from the first cavity 20 to the downstream end portion 17, in the portion excluding the upstream end portion 16 and the side end portions 18 and 19 of the main body 12 of the segment body 11.
- the second cooling passage 22, at the upstream end portion 16, in the cross-sectional view seen from the axial direction of the rotating shaft 5, is aligned so as to overlap in the vertical direction with the first cooling passage 21, is extended as is until the downstream end portion 17 on the downstream in the flow direction of the combustion gas, and opens to the combustion gas space W at a downstream end face 17a.
- upstream end portion 16 of the segment body 11 refers to the portion of the segment body 11 that is sandwiched by an upstream end face 16a and the inner wall 12b on the upstream of the main body 12, and beneath the installation height of the collision plate 14.
- downstream end portion 17 of the segment body 11 refers to the portion of the segment body 11 that is sandwiched by the downstream end face 17a and the inner wall 12b on the downstream of the main body 12, and beneath the installation height of the collision plate 14.
- the first cooling passage 21 has a turn-back structure of turning back at the first cavity 20 to be coupled to the second cooling passage 22, it is possible to select a cooling passage with a long passage length with respect to the axial direction of the rotating shaft 5. That is, the first cooling passage 21 is arranged in the segment body 11 close to the outer circumferential surface side of the upstream end portion 16 of the segment body 11. Meanwhile, the first cooling passage 21 turns back at the first cavity 20 to connect to the second cooling passage 22, and is arranged in the segment body 11 closer to the inner circumferential surface side than the first cooling passage 21 of the upstream end portion 16, and is extended until the downstream end face 17a.
- the longest passage length of the cooling passage of the present embodiment can be selected in the axial direction of the rotating shaft 5 compared to Patent Document 1 and Patent Document 2, and is effective in improving the cooling performance of the segment body.
- first cooling passage 21 and the second cooling passage 22 turn back in the axial direction of the rotating shaft 5 via the first cavity 20, it is possible to put a cooling passage with a long passage length in the main body of the segment body in a compact manner, and it is possible to efficiently cool the segment body.
- a third cooling passage 25 communicating from the cooling space 29 to the combustion gas space W is arranged in a direction approximately perpendicular to the rotating shaft.
- One side of the third cooling passage 25 communicates with the cooling space 29, and the other side opens to the combustion gas space W.
- a second cavity 24 is formed in which one side communicates with the cooling space 29, and the other end side extends in the axial direction of the rotating shaft, with the end being blocked, and a portion of the third cooling passage 25 communicates with the cooling space 29 via the second cavity 24.
- a fourth cooling passage 27 in the side end portion 19 on the downstream of the segment body 11 in the rotation direction R in the same manner as the third cooling passage 25. That is, one side of the fourth cooling passage 27 communicates with the cooling space 29, and the other side opens to the combustion gas space W. Also, in the upstream end portion 16 and the downstream end portion 17, a third cavity 26 is formed in which one side communicates with the cooling space 29, and the other end side extends in the axial direction of the rotating shaft, with the end being blocked, and a portion of the third cooling passage 25 communicates with the cooling space 29 via the third cavity 26. Note that depending on the operation condition of the gas turbine, convection cooling of the side end portion 19 may be omitted without providing a cooling passage in the side end portion 19 on the downstream in the rotation direction R of the aforementioned segment body 11.
- side end portion 18 refers to the portion that is sandwiched by the inner wall 12c of the main body 12 on the upstream of the rotation direction R and the upstream end face 18a, and beneath the installation height of the collision plate 14.
- side end portion 19 refers to the portion that is sandwiched by the inner wall 12c of the main body 12 on the downstream of the rotation direction R and the downstream end face 19a, and beneath the installation height of the collision plate 14.
- cooling air in the present embodiment is described below. As shown in FIG. 2 , a portion of the cooling air CA that is supplied to the turbine 4 is supplied to the reception space 30 via the supply hole 68. The cooling air CA jets into the cooling space 29 via the small holes 15 that are provided in the collision plate 14, and performs impingement cooling of the outer circumferential surface 12a of the main body 12 of the segment body 11.
- a large part of the cooling air CA after the impingement cooling is supplied to the first cooling passage 21 that is provided in the upstream end portion 16, and that opens to the inner wall 12a on the upstream in the flow direction of the combustion gas FG of the main body 12 of the segment body 11, and by flowing in the reverse direction to the flow direction of the combustion gas FG, mainly performs convection cooling of the outer circumferential surface side of the upstream end portion 16, and is then once blown out to the first cavity 20.
- the cooling air CA in the first cavity 20 turns back in the first cavity 20, and in a cross-sectional view seen from the axial direction of the rotating shaft 5, is supplied to the second cooling passage 22 that is provided below the first cooling passage 21. Moreover, the cooling air CA flows toward the downstream end portion 17 of the segment body 11 along the inner circumferential surface 11a of the segment body 11, performs convection cooling mainly of the inner circumferential surface side of the segment body 11, and is discharged to the combustion gas space W from the downstream end face 17a. That is, since it is provided with the turn-back structure as described above, it is possible to select a cooling passage with a long passage length, and is effective in cooling of the segment body.
- the pressure of the combustion gas FG of the segment body 11 changes along the flow direction.
- the pressure is highest in the vicinity of the upstream end face 16a at the upstream of the combustion gas FG flow direction, and the pressure is lowest in the vicinity of the downstream end face 17a at the downstream.
- the cooling air CA from the cooling space 29 flows through the upstream end portion 16 toward the upstream of the flow direction of combustion gas FG, and is discharged from the upstream end face 16a to the combustion gas space W, it is not possible to have a large pressure difference between the pressure of the cooling air CA in the cooling space 29 and the pressure of the combustion gas near the upstream end face 16a. Therefore, in order to sufficiently cool the upstream end portion 16, it is necessary to pass more cooling air that flows through the inside of the first cooling passage 21, which causes an increase in the amount of cooling air by that much.
- the cooling air CA of the cooling space 29 is supplied via the first cooling passage 21 to the first cavity 20, and by being turned back in the first cavity 20 without being discharged as is from the upstream end face 16a to the combustion gas space W, is discharged to the downstream end face 17a via the second cooling passage 22.
- the cooling air that is supplied from the cooling space 29 to the second cavity 24 is supplied through connecting paths 31, but a method of carrying out direct introduction from the cooling space 29 may be used in the same manner as the third cavity 26.
- cooling air having as its object convection cooling of the side end portions 18 and 19 since high pressure cooling air after impingement cooling is supplied to the third cooling passage 25 and the fourth cooling passage 27, it is possible to use the differential pressure between the cooling air of the cooling space 29 and the combustion gas near the side end portion end faces 18a and 19a, and it is effective in cooling of a side edge portion.
- the present embodiment it is possible to adopt the longest cooling passage length in the axial direction of the rotating shaft, and since it is possible to utilize to the utmost the differential pressure of the cooling air, it is most effective for cooling of the segment body.
- the first cooling passage and the second cooling passage are disposed so as to overlap in the vertical direction, the first cooling passage is arranged on the outer circumferential surface side, and the second cooling passage is arranged on the inner circumferential surface side, the cooling performance in the upstream end portion is improved.
- first cooling passage and the second cooling passage are arranged to be mutually parallel with respect to the vertical direction (radial direction of the rotating shaft), and a plurality are arrayed to be parallel at the same hole pitch with respect to the rotation direction R of the rotating shaft, the cooling passages are arranged at the same interval amongst themselves, and the temperature distribution in the upstream end portion becomes smaller, and uniform cooling is possible.
- FIG. 8 shows an arrangement example that differs from the first embodiment, in relation to the first cooling passage and the second cooling passage.
- the first modification compared to the first embodiment, is the same on the point of arranging cooling passages in an annular shape at the same hole pitch with respect to the rotation direction R of the rotating shaft 5, but differs on the point of the second cooling passage 22 having a smaller hole diameter than the first cooling passage 21. Also, it differs on the point of the hole pitch of the second cooling passage 22 in the rotation direction R of the rotating shaft 5 being greater than the hole pitch of the second cooling passage 22 in the rotation direction R.
- cooling of the upstream end portion 16 of the main body 12 in particular is the greatest difficulty, and that which contributes the most to cooling of the main body is the second cooling passage 22.
- the hole diameter of the first cooling passage 21 relatively larger than that of the second cooling passage 22, and reducing the pressure loss in the first cooling passage, the cooling air pressure in the first cavity 20 is made as high as possible.
- the hole diameter of the second cooling passage 22 is smaller than that of the first cooling passage 21, and the hole pitch reduced.
- the pressure loss of the cooling air increases due to the small hole diameter, but since it is possible to utilize the differential pressure with the combustion gas side to the utmost by maintaining the pressure in the first cavity 20 at a high pressure, the cooling efficiency of the entire second cooling passage improves, and compared with the first embodiment, the cooling of the main body (bottom surface) of the segment body is enhanced.
- FIG. 9 shows a partial cross-section of the upstream end portion of the segment body of the second embodiment.
- the present embodiment differs on the point of the first cooling passage having a slope in the axial direction of the rotating shaft with respect to the second cooling passage, and in other aspects is the same as the first embodiment.
- the component elements that are in common with the first embodiment use the same component names and reference numbers as the first embodiment, and detailed descriptions thereof shall be omitted.
- FIG. 9 it is the same as the first embodiment on the point of a second cooling passage 45 being arranged in the axial direction of the rotating shaft 5 along the inner circumferential surface 11a of the segment body 11 until the downstream end face 17a, and being arranged in an annular shape at the same hole pitch in the rotation direction R of the rotating shaft.
- a first cooling passage 44 that communicates with a first cavity 43 having a slope in the axial direction of the rotating shaft 5 heading toward the upstream end face 16a, and intersecting the bottom surface 43a of the first cavity 43 at an angle a.
- the cooling air CA that is blown out from the cooling space 29 to the bottom surface 43a of the first cavity 43 via the first cooling passage 44 acts as impingement cooling air on the bottom surface 43a of the first cavity 43, and so the cooling of the upstream end portion 16 is enhanced compared to the first embodiment.
- the cooling air CA that is introduced from the cooling space 29 flows down the first cooling passage 44 that has a downward slope toward the upstream end portion 16a and reaches the first cavity 43, with the outer circumferential surface side of the upstream end portion 16 being cooled in the interim.
- the cooling air CA by colliding with the bottom surface 43 a of the first cavity 43, imparts an impingement cooling effect on the bottom surface 43a to enhance the cooling of the upstream end portion 16.
- the cooling air CA that turns back from the first cavity 43 flows toward the downstream in the flow direction of the combustion gas FG via the second cooling passage 45, and is discharged to the combustion gas space W from the downstream end portion 17. That is, as shown in FIG. 9 , in the case of the present embodiment, the first cooling passage 44 has with respect to the second cooling passage 45 a downward slope toward the bottom surface 43a of the first cavity 43 in the axial direction of the rotating shaft 5, and thereby the cooling air CA that flows in the first cooling passage 44 imparts an impingement cooling effect in the first cavity 43 compared to the first embodiment. As a result, the cooling of the upstream end portion 16 is enhanced over the entire width of the segment body 11 in the rotation direction R, and the amount of cooling air of the ring segment can be further decreased.
- the present embodiment it is possible to adopt the same constitution as the first modification. That is, it is possible to make the hole diameter of the second cooling passage 45 smaller than the hole diameter of the first cooling passage 44, and make the hole pitch of the second cooling passage 45 in the rotation direction R smaller than the hole pitch of the first cooling passage 44 in the rotation direction R.
- the hole diameter and hole pitch of the respective cooling passages so that the amounts of cooling air that flows through the first cooling passage and the second cooling passage are balanced, it is possible to raise the cooling effect of the main body of the segment body. As a result, since it is possible to reduce the amount of cooling air compared with the first embodiment, the thermal efficiency of the gas turbine is further improved.
- FIG. 10 shows a plan view of the segment body according to the third embodiment.
- the cooling system of the side end portion of the segment body of the ring segment of the present embodiment is different, but other constitutions are the same as the first embodiment.
- a second cavity 24 and a third cavity 26 communicate with the first cavity 20 on the upstream in the gas flow direction of the combustion gas, and communicate with the third cooling passage 25 and the fourth cooling passage 27 on the downstream. That is, the present embodiment differs from the first embodiment on the point of the third cooling passage 25 and the fourth cooling passage 27 being connected to the cooling space 29 via the first cavity 20, the second cavity 24 and the third cavity 26 without being directly coupled to the cooling space 29.
- the cooling performance of the third cooling passage 25 and the fourth cooling passage 27 in the vicinity of the upstream end portion 16 is enhanced compared to the first embodiment. That is, the cooling air CA is supplied from the cooling space 29 to the first cavity 20, and is introduced from the first cavity 20 to the second cavity 24 and the third cavity 26. Furthermore, when discharging the cooling air CA from the second cavity 24 or the third cavity 26 to the combustion gas space W through the third cooling passage 25 or the fourth cooling passage 27, it carries out convection cooling of the side edge portions 18 and 19.
- the upstream end portion 16 that is at the upstream of the flow direction of combustion gas is readily exposed to high temperature combustion gas.
- it is desirable to quicken the flow velocity by raising the pressure of the cooling air that flows through the third cooling passage 25 or the fourth cooling passage 27 in the vicinity of the upstream end portion 16 of the side edge portions 18 and 19.
- the second cavity 24 and the third cavity 26 are directly coupled to the first cavity 20 that is held at a high pressure, the pressure of the cooling air in the vicinity of the upstream end portion 16 is held at a high pressure. Accordingly, the flow velocity of the cooling air that flows through the third cooling passage 25 or the fourth cooling passage 27 in the vicinity of the upstream end portion 16 that are in communication with these is maintained at a high velocity, and the convection cooling is enhanced. Note that depending on the running condition of the gas turbine, for cooling of the side end portion it is possible to provide only the third cooling passage connected to the first cavity via the second cavity, and the fourth cooling passage need not be provided.
- the cooling system of the ring segment of the aforementioned invention it is possible to keep down the amount of cooling air used to the minimum extent, and it is possible to further raise the cooling efficiency and the cooling performance of the segment body 11 and the ring segment 10 that has it as a component element.
- the cooling of the upstream end portion of the ring segment is enhanced, and thermal damage of the ring segment is avoided. Also, it is possible to provide a gas turbine that keeps down the amount used of cooling air to a minimum, and further increases the cooling efficiency and cooling performance of a ring segment. Accordingly, it is possible to improve the reliability and the operating efficiency of a gas turbine.
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Description
- The present invention relates to ring segment with a cooling system of a gas turbine and to a gas turbine.
- Conventionally, since combustion gas of a high temperature and high pressure passes through the turbine of a gas turbine, which is used in the generation of electrical energy, cooling of the ring segment and the like is important in order to continue stabilized operation. In particular, due to improvements in the thermal efficiency of gas turbines in recent years, the temperature of combustion gas continues to increase.
-
FIG. 11 is a cross-sectional view that shows the internal structure relating to the turbine of a gas turbine. The gas turbine supplies combustion gas FG generated in acombustor 3 toturbine vanes 7 andturbine blades 8, and by causing theturbine blades 8 to rotate a rotatingshaft 5, converts rotational energy into electrical power. The turbine vanes 7 and theturbine blades 8 are alternately disposed from the upstream to the downstream of the flow direction of the combustion gas FG. Moreover, a plurality ofturbine blades 8 is disposed in the circumferential direction of the rotatingshaft 5, and thus rotate together with the rotatingshaft 5. - Moreover, the
turbine vanes 7 are disposed on the upstream of theturbine blades 8 in the flow direction of the combustion gas FG, and a plurality are disposed in the circumferential direction of therotating shaft 5, similarly to theturbine blades 8. Aring segment 60 is disposed annularly on the outer periphery side of theturbine blades 8, and between thering segment 60 and theturbine blades 8, a tip clearance is provided in order to avoid mutual interference. -
FIG. 12 is a cross-sectional view of a conventional ring segment. Thering segment 60 is formed from a plurality ofsegment bodies 61, and is oriented annularly in the circumferential direction of therotating shaft 5. Eachsegment body 61 is supported by acasing 67 viahooks 62 of thesegment body 61 and anisolation ring 66. Moreover, acollision plate 64 that is supported from theisolation ring 66 is equipped with a plurality ofsmall holes 65. In thesegment body 61, a plurality ofcooling passages 63 are disposed in the axial direction of the rotatingshaft 5. - In order to cool the
ring segment 60, cooling air CA which is a portion of bleed air of a compressor is supplied to eachsegment body 61 of thering segment 60 from asupply hole 68 of thecasing 67. The cooling air CAjets into the space enclosed by thecollision plate 64 and thesegment body 61, through thesmall holes 65 opened in thecollision plate 64, and carries out impingement cooling of the outer circumferential surface of thesegment body 61. Furthermore, when the cooling air CA after the impingement cooling jets into the combustion gas space from the downstream end of thesegment body 61 in the flow direction of the combustion gas (in the direction from the left side to the right side on the sheet ofFIG. 11 ) via thecooling passage 63, convection cooling of thesegment body 61 is carried out by the cooling air CA that flows through thecooling passage 63. -
Patent Document 1 discloses a ring segment that is provided with the abovementioned collision plate. An example is illustrated in which when the cooling air that has performed impingement cooling is supplied to opening portions that are disposed in the outer circumferential surface of the ring segment (segment body) and discharged from the downstream end of the ring segment in the flow direction of the combustion gas FG to the combustion gas space via the cooling passage (cooling air holes), it cools the ring segment. -
Patent Document 2 discloses a structure that is an improvement on that disclosed inPatent Document 1. A cooling passage (first passage) that jets a portion of cooling air that has performed impingement cooling from the upstream end of the ring segment (segment body) in the flow direction of the combustion gas to the combustion gas space is disclosed, and a cooling passage (second passage) that jets a greater part of the remaining cooling air after the impingement cooling from the downstream end in the flow direction of the combustion gas to the combustion gas space is disclosed. Thereby, cooling of the ring segment is enhanced. -
- [Patent Document 1]
JP H11-22411A - [Patent Document 2]
JP 2004-100682 A - However, in the invention disclosed in
Patent Document 1, there is a region in which a cooling passage is not disposed on the upstream end portion of the ring segment in the flow direction of the combustion gas, and so in the case of the combustion gas further increasing in temperature, the problem arises of the upstream end portion of the ring segment being damaged thermally out by the high temperature combustion gas. - Also, in the invention disclosed in
Patent Document 2, when a portion of the cooling air after the impingement cooling is discharged from the upstream end portion of the ring segment in the flow direction of the combustion gas to the combustion gas space via the cooling passage (cooling air holes), it enhances the cooling of the upstream end portion of the ring segment. However, since the cooling air that is discharged to the upstream end side of the ring segment in the flow direction of the combustion gas is discharged to the combustion gas space cooling only the upstream end portion, the problem arises of it becoming a loss of the amount of cooling air, and an increase in the amount of cooling air leads to a reduction in the thermal efficiency of the gas turbine. - The present invention was achieved in view of the above problems, and has as its object to provide a cooling system of a ring segment that has as its object to prevent thermal damage of the ring segment as the combustion gas increases in temperature and improve the thermal efficiency by reducing the amount of cooling air, and a gas turbine.
- The present invention adopts a ring segment with a cooling system having the features of
claim 1 to solve the aforementioned problem points. Preferred embodiments of the ring segment are defined in the dependent claims. - That is, the cooling system of ring segment of the present invention is a ring segment cooling system that is formed from a plurality of segment bodies that are arranged in the circumferential direction to form a ring shape, and that cools a ring segment of a gas turbine that is arranged in a casing so that the inner peripheral surface is kept a fixed distance from the tips of turbine blades, is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that is arranged in the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a combustion gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.
- The present invention provides the first cavity in the upstream end portion of the ring segment in the flow direction of the combustion gas, and since the cooling air of the cooling space is supplied to the first cavity via the first cooling passage, and furthermore discharged to the combustion gas space from the downstream end portion in the flow direction of the combustion gas via the second cooling passage, the length of the cooling passage is elongated, and the convection cooling of the upstream end portion of the segment body which has an intense heat load is enhanced. For that reason, thermal damage of the upstream end portion of the segment body by the high temperature combustion gas is avoided.
- In the cooling system of ring segment of the present invention, it is preferable that the first cooling passage and the second cooling passage have a structure of turning back in the axial direction of the rotating shaft in the first cavity.
- According to the present invention, since the first cooling passage and the second cooling passage have a structure of turning back in the flow direction of the combustion gas in the first cavity, the entirety of the cooling passage with a long passage length is put in the main body of the segment body in a compact manner, and miniaturization of the ring segment is achieved.
- In the cooling system of ring segment of the present invention, it is preferable that the first cooling passage and the second cooling passage each be arranged in a plurality in an annular shape with respect to the rotation direction of the rotating shaft, and be arranged so as to be mutually parallel in the radial direction.
- According to the present invention, since the first cooling passage and the second cooling passage are arranged so as to be mutually parallel, the distance between adjacent cooling passages is uniformly maintained, the temperature distribution of the upstream end portion diminishes, and the cooling performance of the upstream end portion of the segment body improves.
- In the cooling system of ring segment of the present invention, it is preferable that the first cooling passage and the second cooling passage each be arranged in a plurality in an annular shape with respect to the rotation direction of the rotating shaft, and the first cooling passage be arranged sloping in the rotation direction of the rotating shaft with respect to the second cooling passage.
- According to the present invention, since the cooling air that is supplied to the first cavity via the first cooling passage jets toward the bottom surface of the first cavity, and performs impingement cooling of the bottom surface of the first cavity, it is effective for cooling of the upstream end portion of the segment body where the heat load is intense.
- In the cooling system of ring segment of the present invention, it is preferable that the first cooling passage has a shorter length than the second cooling passage and be disposed further to the outer circumferential surface side of the main body than the second cooling passage.
- According to the present invention, since the fist cooling passage is arranged at the outer circumferential surface side of the upstream end portion, and the second cooling passage is arranged at the inner circumferential surface side of the upstream end portion, the outer circumferential surface side and the inner circumferential surface side of the upstream end portion of the segment body are cooled together, and the cooling performance of the upstream end portion of the segment body improves.
- In the cooling system of ring segment of the present invention, it is preferable that the hole diameter of the second cooling passage be smaller than the hole diameter of the first cooling passage.
- According to the present invention, since it is possible to maintain a high pressure in the first cavity, it is possible to increase the velocity of the cooling air that flows through the second cooling passage, and the cooling performance of the inner circumferential surface side of the segment body improves.
- In the cooling system of ring segment of the present invention, it is preferable that the hole pitch of the second cooling passage in the rotation direction of the rotating shaft be smaller than the hole pitch of the first cooling passage in the rotation direction of the rotating shaft.
- According to the present invention, since the hole pitch of the second cooling passage in the rotation direction of the rotating shaft is smaller compared to the first cooling passage, the cooling effect of the second cooling passage is high, and the cooling performance of the segment body improves.
- In the cooling system of ring segment of the present invention, it is preferable that a third cooling passage be arranged at the side end portion on the upstream of the segment body in the rotation direction of the rotating shaft, and that it communicate from the cooling space to the combustion gas space in the side end portion on the upstream of the segment body in the rotation direction of the rotating shaft.
- According to the present invention, the convection cooling of the side end portion on the upstream of the segment body in the rotation direction of the rotating shaft is enhanced.
- In the cooling system of ring segment of the present invention, it is preferable that a fourth cooling passage be arranged at the side end portion on the downstream of the segment body in the rotation direction of the rotating shaft, and that it communicate from the cooling space to the combustion gas space in the side end portion on the downstream of the segment body in the rotation direction of the rotating shaft.
- According to the present invention, since providing the fourth cooling passage cools the side end portions of both sides of the upstream and the downstream of the segment body in the rotation direction of the rotating shaft, the convection cooling of the segment body is enhanced.
- In the cooling system of ring segment of the present invention, it is preferable that the third cooling passage or the fourth cooling passage communicate with the first cavity via the second cavity or the third cavity.
- According to the present invention, since a portion of the high pressure cooling air that is supplied to the first cavity is supplied to the third cooling passage of the fourth cooling passage via the second cavity or the third cavity, the cooling performance of the third cooling passage or the fourth cooling passage in the vicinity of the upstream end portion is enhanced.
- A gas turbine of the present invention is preferably provided with the aforementioned cooling system of ring segment.
- According to the present invention, the amount of cooling air of the gas turbine is reduced, and the thermal efficiency of the gas turbine improves.
- According the aforementioned present invention, the cooling of the upstream end portion of the ring segment is enhanced, and thermal damage of the ring segment is avoided. Also, it is possible to provide a gas turbine that keeps down the amount used of cooling air to a minimum, and further increases the cooling efficiency and cooling performance of a ring segment. Accordingly, it is possible to improve the reliability and the operating efficiency of a gas turbine.
-
- [
FIG. 1] FIG. 1 shows the overall configuration of a gas turbine according to the present invention. - [
FIG. 2] FIG. 2 shows the essential portion cross-sectional view of the ring segment of the first embodiment. - [
FIG. 3] FIG. 3 shows a perspective view of the segment body of the first embodiment. - [
FIG. 4] FIG. 4 shows a plan view of the segment body of the first embodiment. - [
FIG. 5] FIG. 5 shows a cross-sectional view along line A-A of the segment body shown inFIG. 4 . - [
FIG. 6] FIG. 6 shows a cross-sectional view along line B-B of the segment body shown inFIG. 4 . - [
FIG. 7] FIG. 7 shows a cross-sectional view along line C-C of the segment body shown inFIG. 4 . - [
FIG. 8] FIG. 8 shows a cross-sectional view along line C-C of the segment body of the first modification. - [
FIG. 9] FIG. 9 shows a partial cross-sectional view of the upstream end portion of the segment body of the second embodiment. - [
FIG. 10] FIG. 10 is a plan view of the segment body of the third embodiment. - [
FIG. 11] FIG. 11 shows the cross-sectional structure of the turbine. - [
FIG. 12] FIG. 12 shows the essential portion cross-sectional view of a ring segment of a conventional example. - Hereinbelow, regarding the cooling system of ring segment and gas turbine of the present invention, the embodiments thereof shall be described based on
FIG. 1 to FIG. 11 . - A description of the first embodiment shall be given based on
FIGS. 1 to 7 andFIG. 11 . -
FIG. 1 is an overall configuration diagram of the gas turbine. Agas turbine 1 has as main constituent elements acompressor 2 that compresses combustion air, acombustor 3 that injects fuel FL into the combustion air that is sent from thecompressor 2, causes a combustion, and generates combustion gas, a turbine 4 that is positioned on the downstream of thiscombustor 3 and driven by the combustion gas that has left thecombustor 3, agenerator 6, and arotating shaft 5 that integrally couples thecompressor 2, the turbine 4, and thegenerator 6. - Since the turbine 4 has the same constitution as the content described in
FIG. 11 of the background art, a detailed description thereof shall be omitted. The same names and reference numerals shall be used for common component names and reference numerals. -
FIG. 2 shows a cross section of the essential portions of the ring segment of the gas turbine. - A
ring segment 10 is a constituent member of the turbine 4 that is supported by thecasing 67, and is constituted by a plurality ofsegment bodies 11 that are arranged in the circumferential direction of arotating shaft 5 to form a ring shape. Thesegment bodies 11 are positioned so that a fixed clearance is secured between the innerperipheral surface 11a of the segment bodies and atip 8a of arotor blade 8. Thering segment 10 is formed for example from a heat-resistant nickel alloy or the like. Note that thereference numeral 7 in the drawing denotes turbine vanes of the turbine 4. - In the
segment body 11, the main constituent elements are a main body (bottom plate) 12, hooks 13, and acollision plate 14. Thesegment body 11 is attached to aisolation ring 28 via thehooks 13 that are provided on the upstream and downstream in the flow direction of the combustion gas FG, and is supported by thecasing 67 via aisolation ring 28. Thesegment body 11 is provided with themain body 12, thecollision plate 14, thehooks 13 that are arranged on the upstream and downstream in the flow direction of the combustion gas FG, and a cooling space (hereinbelow called a "cooling space") 29 that is enclosed byside end portions 18 an 19 (refer toFIG. 4 ) that are provided on the upstream and downstream of the direction that is approximately perpendicular with the axial direction of the rotating shaft 5 (the rotation direction of the rotating shaft 5). The coolingspace 29 is formed in thesegment body 11, and is a space that is in contact with an outercircumferential surface 12a side of themain body 12 that is positioned on the rear surface (outer peripheral surface), viewing from the innerperipheral surface 11a of thesegment body 11. - The
collision plate 14 is installed on the upper portion of the coolingspace 29. A large number of thesmall holes 15 through which the cooling air CA for impingement cooling passes are bored in thecollision plate 14. Above thecollision plate 14, areception space 30 is arranged in which cooling air CA in thecasing 67 is introduced via asupply hole 68. The cooling air CA that is supplied to thereception space 30 jets from thesmall holes 15 in the state of the entirety being equalized to approximately the same pressure, and performs impingement cooling of the inner circumferential surface (outercircumferential surface 12a of the main body 12) of the coolingspace 29. -
FIG. 3 is a perspective view of thesegment body 11. The combustion gas FG flows in the direction from the left side to the right side on the sheet surface, and the rotation direction (rotation direction of the turbine blades) R of therotating shaft 5 is a direction that is perpendicular to the axial direction of the rotating shaft. As stated above, thesegment body 11 is supported by theisolation ring 28 via thehooks 13. Also, in the center of thesegment body 11, thecollision plate 14 is fixed toinner walls 12b of themain body 12 of thesegment body 11. - The
collision plate 14 has a shape in which thecenter portion 14a is indented in a concave shape from theperiphery 14b. That is, since themain body 12 of thesegment body 11 is placed in a higher temperature state than thecollision plate 14, thermal elongation becomes larger than thecollision plate 14 in the axial direction of the rotating shaft and the rotation direction R of the rotating shaft. For that reason, thecollision plate 14 is pulled from theinner wall 12b side of themain body 12, and thermal stress occurs in thecollision plate 14. However, by providing the indentation in a concave shape in thecenter portion 14a of thecollision plate 14, the flexibility of theentire collision plate 14 increases, and so there is the effect of the thermal stress that is generated being eased. Even in the case of thecenter portion 14a of thecollision plate 14 being formed in a concave shape, there is the same effect. Note that in order to make the impingement cooling uniform over the entire surface of the outercircumferential surface 12a of themain body 12, it is desirable to provide thesmall holes 15 not only in thecenter portion 14a of thecollision plate 14 but also in theperiphery 14b. -
FIG. 4 is a plan view of the segment body viewed in the direction of the rotating shaft from the collision plate side of thesegment body 11. In thesegment body 11 of the present embodiment, at theupstream end portion 16 on the upstream in the flow direction of the combustion gas FG, afirst cavity 20 is arranged in a direction approximately perpendicular to the axial direction of therotating shaft 5. Also, a cooling passage (first cooling passage) 21 that couples the coolingspace 29 and thefirst cavity 20 is provided in the axial direction of therotating shaft 5, and a cooling passage (second cooling passage) 22 that opens from thefirst cavity 20 to adownstream end portion 17 of the downstream in the flow direction of the combustion gas FG is arranged in the axial direction of the rotating shaft. Thefirst cavity 20 plays the role of a manifold that mutually couples thefirst cooling passage 21 and thesecond cooling passage 22. -
FIG. 5 shows a cross section of the segment body shown inFIG. 4 (cross section along line A-A), andFIG. 6 shows a side view (cross section along line B-B).FIG. 7 shows a cross section of the segment body viewed from the axial direction of the rotating shaft 5 (cross section along line C-C). - The structures of the
first cooling passage 21 and thesecond cooling passage 22 shall be described with reference toFIG. 4 to FIG. 7 . In theupstream end portion 16 on the upstream of the flow direction of the combustion gas FG with respect to the segment body 11 (the direction heading from the left side to the right side on the sheet surface inFIG. 4 ), thefirst cooling passage 21 and thesecond cooling passage 22 are both bored so as to pass through the cross section of themain body 12 of thesegment body 11 in the axial direction of therotating shaft 5. - Also, as shown in
FIG. 7 , thefirst cooling passage 21 and thesecond cooling passage 22 are arranged in parallel at a regular interval so as to mutually form one row in the vertical direction (the diameter direction of the rotating shaft 5), in the cross-sectional view seen from the axial direction of therotating shaft 5. Also, for both thefirst cooling passage 21 and thesecond cooling passage 22, a plurality of thecooling passages rotating shaft 5. That is, at theupstream end portion 16 of thesegment body 11, thefirst cooling passage 21 and thesecond cooling passage 22 are arranged so as to overlap in two rows in the vertical direction from theside end portion 18 on the upstream in the rotation direction R of thesegment body 11 to theside end portion 19 on the downstream. Also, as for thefirst cooling passage 21 and thesecond cooling passage 22, adjacent cooling passages are arranged at a predetermined hole pitch so as to be mutually parallel in the rotation direction R of therotating shaft 5. Furthermore, thefirst cooling passage 21 and thesecond cooling passage 22 are arranged so as to be mutually parallel in the axial direction of therotating shaft 5. - Also, the cooling passage that is arranged in the axial direction of the rotating shaft 5 (second cooling passage 22) is provided along the inner
circumferential surface 11a of thesegment body 11, from thefirst cavity 20 to thedownstream end portion 17, in the portion excluding theupstream end portion 16 and theside end portions main body 12 of thesegment body 11. Thesecond cooling passage 22, at theupstream end portion 16, in the cross-sectional view seen from the axial direction of therotating shaft 5, is aligned so as to overlap in the vertical direction with thefirst cooling passage 21, is extended as is until thedownstream end portion 17 on the downstream in the flow direction of the combustion gas, and opens to the combustion gas space W at adownstream end face 17a. Note that theupstream end portion 16 of thesegment body 11 refers to the portion of thesegment body 11 that is sandwiched by anupstream end face 16a and theinner wall 12b on the upstream of themain body 12, and beneath the installation height of thecollision plate 14. Also, note that thedownstream end portion 17 of thesegment body 11 refers to the portion of thesegment body 11 that is sandwiched by thedownstream end face 17a and theinner wall 12b on the downstream of themain body 12, and beneath the installation height of thecollision plate 14. - With the constitution of the first cooling passage and the second cooling passage as described above, since the
first cooling passage 21 has a turn-back structure of turning back at thefirst cavity 20 to be coupled to thesecond cooling passage 22, it is possible to select a cooling passage with a long passage length with respect to the axial direction of therotating shaft 5. That is, thefirst cooling passage 21 is arranged in thesegment body 11 close to the outer circumferential surface side of theupstream end portion 16 of thesegment body 11. Meanwhile, thefirst cooling passage 21 turns back at thefirst cavity 20 to connect to thesecond cooling passage 22, and is arranged in thesegment body 11 closer to the inner circumferential surface side than thefirst cooling passage 21 of theupstream end portion 16, and is extended until thedownstream end face 17a. As a result, the longest passage length of the cooling passage of the present embodiment can be selected in the axial direction of therotating shaft 5 compared toPatent Document 1 andPatent Document 2, and is effective in improving the cooling performance of the segment body. - Also, since there is a structure in which the
first cooling passage 21 and thesecond cooling passage 22 turn back in the axial direction of therotating shaft 5 via thefirst cavity 20, it is possible to put a cooling passage with a long passage length in the main body of the segment body in a compact manner, and it is possible to efficiently cool the segment body. - Next, the structure of a cooling path that is provided in the
side end portions segment body 11 shall be described. - As shown in
FIG. 4 , in theside end portion 18 on the upstream of thesegment body 11 in the rotation direction R of the rotating shaft, athird cooling passage 25 communicating from the coolingspace 29 to the combustion gas space W is arranged in a direction approximately perpendicular to the rotating shaft. One side of thethird cooling passage 25 communicates with the coolingspace 29, and the other side opens to the combustion gas space W. Also, in theupstream end portion 16 and thedownstream end portion 17, asecond cavity 24 is formed in which one side communicates with the coolingspace 29, and the other end side extends in the axial direction of the rotating shaft, with the end being blocked, and a portion of thethird cooling passage 25 communicates with the coolingspace 29 via thesecond cavity 24. - In the present embodiment, it is possible to also constitute a
fourth cooling passage 27 in theside end portion 19 on the downstream of thesegment body 11 in the rotation direction R in the same manner as thethird cooling passage 25. That is, one side of thefourth cooling passage 27 communicates with the coolingspace 29, and the other side opens to the combustion gas space W. Also, in theupstream end portion 16 and thedownstream end portion 17, athird cavity 26 is formed in which one side communicates with the coolingspace 29, and the other end side extends in the axial direction of the rotating shaft, with the end being blocked, and a portion of thethird cooling passage 25 communicates with the coolingspace 29 via thethird cavity 26. Note that depending on the operation condition of the gas turbine, convection cooling of theside end portion 19 may be omitted without providing a cooling passage in theside end portion 19 on the downstream in the rotation direction R of theaforementioned segment body 11. - Note that the
side end portion 18 refers to the portion that is sandwiched by theinner wall 12c of themain body 12 on the upstream of the rotation direction R and theupstream end face 18a, and beneath the installation height of thecollision plate 14. Also, theside end portion 19 refers to the portion that is sandwiched by theinner wall 12c of themain body 12 on the downstream of the rotation direction R and thedownstream end face 19a, and beneath the installation height of thecollision plate 14. - The flow of cooling air in the present embodiment is described below. As shown in
FIG. 2 , a portion of the cooling air CA that is supplied to the turbine 4 is supplied to thereception space 30 via thesupply hole 68. The cooling air CA jets into the coolingspace 29 via thesmall holes 15 that are provided in thecollision plate 14, and performs impingement cooling of the outercircumferential surface 12a of themain body 12 of thesegment body 11. A large part of the cooling air CA after the impingement cooling is supplied to thefirst cooling passage 21 that is provided in theupstream end portion 16, and that opens to theinner wall 12a on the upstream in the flow direction of the combustion gas FG of themain body 12 of thesegment body 11, and by flowing in the reverse direction to the flow direction of the combustion gas FG, mainly performs convection cooling of the outer circumferential surface side of theupstream end portion 16, and is then once blown out to thefirst cavity 20. - The cooling air CA in the
first cavity 20 turns back in thefirst cavity 20, and in a cross-sectional view seen from the axial direction of therotating shaft 5, is supplied to thesecond cooling passage 22 that is provided below thefirst cooling passage 21. Moreover, the cooling air CA flows toward thedownstream end portion 17 of thesegment body 11 along the innercircumferential surface 11a of thesegment body 11, performs convection cooling mainly of the inner circumferential surface side of thesegment body 11, and is discharged to the combustion gas space W from thedownstream end face 17a. That is, since it is provided with the turn-back structure as described above, it is possible to select a cooling passage with a long passage length, and is effective in cooling of the segment body. - Meanwhile, the pressure of the combustion gas FG of the
segment body 11 changes along the flow direction. The pressure is highest in the vicinity of theupstream end face 16a at the upstream of the combustion gas FG flow direction, and the pressure is lowest in the vicinity of thedownstream end face 17a at the downstream. Namely, in the example shown in thePatent Document 2, since the cooling air CA from the coolingspace 29 flows through theupstream end portion 16 toward the upstream of the flow direction of combustion gas FG, and is discharged from theupstream end face 16a to the combustion gas space W, it is not possible to have a large pressure difference between the pressure of the cooling air CA in the coolingspace 29 and the pressure of the combustion gas near theupstream end face 16a. Therefore, in order to sufficiently cool theupstream end portion 16, it is necessary to pass more cooling air that flows through the inside of thefirst cooling passage 21, which causes an increase in the amount of cooling air by that much. - On the other hand, in the case of the present embodiment, in order to cool the
upstream end portion 16, the cooling air CA of the coolingspace 29 is supplied via thefirst cooling passage 21 to thefirst cavity 20, and by being turned back in thefirst cavity 20 without being discharged as is from theupstream end face 16a to the combustion gas space W, is discharged to thedownstream end face 17a via thesecond cooling passage 22. That is, since the cooling air CA is discharged to the combustion gas space W at thedownstream end face 17a where the combustion gas pressure is the lowest, since it is possible to utilize to the utmost the pressure differential between the cooling air in the coolingspace 29 and the combustion gas in the vicinity of thedownstream end face 17a, it is possible to increase the flow velocity in the cooling passage, and it is possible to substantially reduce the amount of cooling air, compared to the examples ofPatent Document 1 andPatent Document 2. - On the other hand, in the
side end portions segment body 11, when a portion of the cooling air CA which has carried out impingement cooling in the coolingspace 29 is discharged to the combustion gas space W through thethird cooling passage 25 and thefourth cooling passage 27, it carries out convection cooling of theside edge portions side end portions space 29 is once supplied to thesecond cavities third cooling passages second cavities third cooling passage 25 to the combustion gas space W, convection cooling of theside end portions - Note that in the embodiment shown in
FIG. 4 , the cooling air that is supplied from the coolingspace 29 to thesecond cavity 24 is supplied through connectingpaths 31, but a method of carrying out direct introduction from the coolingspace 29 may be used in the same manner as thethird cavity 26. - As for cooling air having as its object convection cooling of the
side end portions third cooling passage 25 and thefourth cooling passage 27, it is possible to use the differential pressure between the cooling air of the coolingspace 29 and the combustion gas near the side end portion end faces 18a and 19a, and it is effective in cooling of a side edge portion. - According to the present embodiment, it is possible to adopt the longest cooling passage length in the axial direction of the rotating shaft, and since it is possible to utilize to the utmost the differential pressure of the cooling air, it is most effective for cooling of the segment body.
- Also, in the upstream end portion, since the first cooling passage and the second cooling passage are disposed so as to overlap in the vertical direction, the first cooling passage is arranged on the outer circumferential surface side, and the second cooling passage is arranged on the inner circumferential surface side, the cooling performance in the upstream end portion is improved.
- Also, since the first cooling passage and the second cooling passage are arranged to be mutually parallel with respect to the vertical direction (radial direction of the rotating shaft), and a plurality are arrayed to be parallel at the same hole pitch with respect to the rotation direction R of the rotating shaft, the cooling passages are arranged at the same interval amongst themselves, and the temperature distribution in the upstream end portion becomes smaller, and uniform cooling is possible.
-
FIG. 8 shows an arrangement example that differs from the first embodiment, in relation to the first cooling passage and the second cooling passage. The first modification, compared to the first embodiment, is the same on the point of arranging cooling passages in an annular shape at the same hole pitch with respect to the rotation direction R of therotating shaft 5, but differs on the point of thesecond cooling passage 22 having a smaller hole diameter than thefirst cooling passage 21. Also, it differs on the point of the hole pitch of thesecond cooling passage 22 in the rotation direction R of therotating shaft 5 being greater than the hole pitch of thesecond cooling passage 22 in the rotation direction R. If these hole diameters and hole pitches of thefirst cooling passage 21 and thesecond cooling passage 22 are adopted, a sufficient amount of the cooling air that is supplied to the second cooling passage is secured for cooling, and compared to the first embodiment, the cooling performance of the main body (bottom surface) side of the segment body is improved. - That is, in the main body of the segment body, cooling of the
upstream end portion 16 of themain body 12 in particular is the greatest difficulty, and that which contributes the most to cooling of the main body is thesecond cooling passage 22. In order to improve the cooling performance of the ring segment, it is desirable to adopt a small hole diameter as the cooling passage, and make the hole pitch narrow. In the case of the present modification, by making the hole diameter of thefirst cooling passage 21 relatively larger than that of thesecond cooling passage 22, and reducing the pressure loss in the first cooling passage, the cooling air pressure in thefirst cavity 20 is made as high as possible. Meanwhile, the hole diameter of thesecond cooling passage 22 is smaller than that of thefirst cooling passage 21, and the hole pitch reduced. As a result, in thesecond cooling passage 22, the pressure loss of the cooling air increases due to the small hole diameter, but since it is possible to utilize the differential pressure with the combustion gas side to the utmost by maintaining the pressure in thefirst cavity 20 at a high pressure, the cooling efficiency of the entire second cooling passage improves, and compared with the first embodiment, the cooling of the main body (bottom surface) of the segment body is enhanced. -
FIG. 9 shows a partial cross-section of the upstream end portion of the segment body of the second embodiment. - Compared to the first embodiment, the present embodiment differs on the point of the first cooling passage having a slope in the axial direction of the rotating shaft with respect to the second cooling passage, and in other aspects is the same as the first embodiment. Note that the component elements that are in common with the first embodiment use the same component names and reference numbers as the first embodiment, and detailed descriptions thereof shall be omitted.
- In
FIG. 9 , it is the same as the first embodiment on the point of asecond cooling passage 45 being arranged in the axial direction of therotating shaft 5 along the innercircumferential surface 11a of thesegment body 11 until thedownstream end face 17a, and being arranged in an annular shape at the same hole pitch in the rotation direction R of the rotating shaft. However, it differs on the point of afirst cooling passage 44 that communicates with afirst cavity 43 having a slope in the axial direction of therotating shaft 5 heading toward theupstream end face 16a, and intersecting thebottom surface 43a of thefirst cavity 43 at an angle a. Note that it is the same as the first embodiment on the point of a plurality of the cooling passages being arranged in an annular shape along the innercircumferential surface 11a of thesegment body 11 with respect to the rotation direction R of the rotating shaft for both thefirst cooling passage 44 and thesecond cooling passage 45. - According to the aforementioned constitution, the cooling air CA that is blown out from the cooling
space 29 to thebottom surface 43a of thefirst cavity 43 via thefirst cooling passage 44 acts as impingement cooling air on thebottom surface 43a of thefirst cavity 43, and so the cooling of theupstream end portion 16 is enhanced compared to the first embodiment. - That is, the cooling air CA that is introduced from the cooling
space 29 flows down thefirst cooling passage 44 that has a downward slope toward theupstream end portion 16a and reaches thefirst cavity 43, with the outer circumferential surface side of theupstream end portion 16 being cooled in the interim. Moreover, the cooling air CA, by colliding with thebottom surface 43 a of thefirst cavity 43, imparts an impingement cooling effect on thebottom surface 43a to enhance the cooling of theupstream end portion 16. - The cooling air CA that turns back from the
first cavity 43 flows toward the downstream in the flow direction of the combustion gas FG via thesecond cooling passage 45, and is discharged to the combustion gas space W from thedownstream end portion 17. That is, as shown inFIG. 9 , in the case of the present embodiment, thefirst cooling passage 44 has with respect to the second cooling passage 45 a downward slope toward thebottom surface 43a of thefirst cavity 43 in the axial direction of therotating shaft 5, and thereby the cooling air CA that flows in thefirst cooling passage 44 imparts an impingement cooling effect in thefirst cavity 43 compared to the first embodiment. As a result, the cooling of theupstream end portion 16 is enhanced over the entire width of thesegment body 11 in the rotation direction R, and the amount of cooling air of the ring segment can be further decreased. - Also, in the present embodiment, it is possible to adopt the same constitution as the first modification. That is, it is possible to make the hole diameter of the
second cooling passage 45 smaller than the hole diameter of thefirst cooling passage 44, and make the hole pitch of thesecond cooling passage 45 in the rotation direction R smaller than the hole pitch of thefirst cooling passage 44 in the rotation direction R. - By selecting the hole diameter and hole pitch of the respective cooling passages so that the amounts of cooling air that flows through the first cooling passage and the second cooling passage are balanced, it is possible to raise the cooling effect of the main body of the segment body. As a result, since it is possible to reduce the amount of cooling air compared with the first embodiment, the thermal efficiency of the gas turbine is further improved.
-
FIG. 10 shows a plan view of the segment body according to the third embodiment. - Compared to the first embodiment, the cooling system of the side end portion of the segment body of the ring segment of the present embodiment is different, but other constitutions are the same as the first embodiment.
- Note that the component elements that are in common with the first embodiment use the same component names and reference numbers as the first embodiment, and detailed descriptions thereof shall be omitted.
- In the present embodiment, a
second cavity 24 and athird cavity 26 communicate with thefirst cavity 20 on the upstream in the gas flow direction of the combustion gas, and communicate with thethird cooling passage 25 and thefourth cooling passage 27 on the downstream. That is, the present embodiment differs from the first embodiment on the point of thethird cooling passage 25 and thefourth cooling passage 27 being connected to the coolingspace 29 via thefirst cavity 20, thesecond cavity 24 and thethird cavity 26 without being directly coupled to the coolingspace 29. - According to the present embodiment, the cooling performance of the
third cooling passage 25 and thefourth cooling passage 27 in the vicinity of theupstream end portion 16 is enhanced compared to the first embodiment. That is, the cooling air CA is supplied from the coolingspace 29 to thefirst cavity 20, and is introduced from thefirst cavity 20 to thesecond cavity 24 and thethird cavity 26. Furthermore, when discharging the cooling air CA from thesecond cavity 24 or thethird cavity 26 to the combustion gas space W through thethird cooling passage 25 or thefourth cooling passage 27, it carries out convection cooling of theside edge portions - In particular, the
upstream end portion 16 that is at the upstream of the flow direction of combustion gas is readily exposed to high temperature combustion gas. In order to enhance the cooling performance of theside edge portions third cooling passage 25 or thefourth cooling passage 27 in the vicinity of theupstream end portion 16 of theside edge portions - However, in the case of the first embodiment, since the end of the
second cavity 24 or thethird cavity 26 that extend toward theupstream end face 16a is blocked, the terminal pressure in the cavity is hindered from increasing. For that reason, there is a limit to increasing the flow velocity of the cooling air that flows through thethird cooling passage 25 or thefourth cooling passage 27 that communicates with thesecond cavity 24 or thethird cavity 26. - On the other hand, in the present embodiment, since the
second cavity 24 and thethird cavity 26 are directly coupled to thefirst cavity 20 that is held at a high pressure, the pressure of the cooling air in the vicinity of theupstream end portion 16 is held at a high pressure. Accordingly, the flow velocity of the cooling air that flows through thethird cooling passage 25 or thefourth cooling passage 27 in the vicinity of theupstream end portion 16 that are in communication with these is maintained at a high velocity, and the convection cooling is enhanced. Note that depending on the running condition of the gas turbine, for cooling of the side end portion it is possible to provide only the third cooling passage connected to the first cavity via the second cavity, and the fourth cooling passage need not be provided. - According to the cooling system of the ring segment of the aforementioned invention, it is possible to keep down the amount of cooling air used to the minimum extent, and it is possible to further raise the cooling efficiency and the cooling performance of the
segment body 11 and thering segment 10 that has it as a component element. - According to the cooling system of the ring segment of the present invention, the cooling of the upstream end portion of the ring segment is enhanced, and thermal damage of the ring segment is avoided. Also, it is possible to provide a gas turbine that keeps down the amount used of cooling air to a minimum, and further increases the cooling efficiency and cooling performance of a ring segment. Accordingly, it is possible to improve the reliability and the operating efficiency of a gas turbine.
-
- 1 gas turbine
- 2 compressor
- 3 combustor
- 4 turbine
- 5 rotating shaft
- 6 generator
- 7 turbine vanes
- 8 turbine blades
- 10, 40, 50, 60 ring segment
- 11, 41, 51, 61 segment body
- 12, 42 main body
- 13 hook
- 14, 64 collision plate
- 15, 65 small hole
- 16 upstream end portion (upstream of combustion gas flow direction)
- 16a upstream end face (upstream of combustion gas flow direction)
- 17 downstream end portion (downstream of combustion gas flow direction)
- 17a downstream end face (downstream of combustion gas flow direction)
- 18 side end portion (upstream in rotation direction)
- 18a side portion end face (upstream in rotation direction)
- 19 side end portion (downstream in rotation direction)
- 19a side portion end face (downstream in rotation direction)
- 20, 43 cavity (first cavity)
- 21, 44 cooling passage (first cooling passage)
- 22, 45 cooling passage (second cooling passage)
- 24 cavity (second cavity)
- 25 cooling passage (third cooling passage)
- 26 cavity (third cavity)
- 27 cooling passage (fourth cooling passage)
- 28 isolation ring
- 29 cooling space
- 30 reception space
- 31 connecting path
- 66 isolation ring
- 67 casing
- 68 supply hole
- R rotation direction of rotating shaft
- W combustion gas space
- CA cooling gas
- FG combustion gas
- FL fuel
Claims (11)
- A ring segment (10;40;50) with a cooling system that is formed from a plurality of segment bodies (11;41;51) that are to be arranged in a casing (67) of a gas turbine (1) in the circumferential direction of a rotating shaft (5) of the gas turbine (1) to form a ring shape, each segment body (11;41;51) of the ring segment (10;40;50) respectively comprising:a cooling space (29) which is formed in the segment body (11;41;51) so as to be adjacent to an outer circumferential surface (12a) of a main body (12;42) of the segment body (11;41;51);a first cavity (20;43) that is arranged at an upstream end portion (16) of the segment body (11;41;51) in an axial direction of the ring segment (10;40;50) and so as to extend in a circumferential direction of the ring segment (10;40;50);a plurality of first cooling passages (21;44) that communicate from the cooling space (29) to the first cavity (20;43); anda plurality of second cooling passages (22;45) that are provided along an inner circumferential surface (11a) of the segment body (11;41;51) and communicate from the first cavity (20;43) to a combustion gas space (W) at a downstream end portion (17) of the segment body (11;41;51) in the axial direction of the ring segment (10;40;50).
- The ring segment (10;40;50) according to claim 1, wherein
the first cooling passage (21;44) and the second cooling passage (22;45) have a structure of turning back in the first cavity (20;43) in the axial direction of the ring segment (10; 40; 50). - The ring segment (50) according to claim 1 or claim 2, wherein
the first cooling passage (21) and the second cooling passage (22) each is arranged in a plurality in an annular shape with respect to the circumferential direction of the ring segment (50), and is arranged so as to be mutually parallel in a radial direction of the ring segment (50). - The ring segment (40) according to claim 1 or claim 2, wherein
the first cooling passage (44) and the second cooling passage (45) are arranged in a plurality in an annular shape with respect to the circumferential direction of the ring segment (40), and the first cooling passage (44) is arranged sloping in the rotation direction (R) of the rotating shaft (5) with respect to the second cooling passage (45). - The ring segment (10;40;50) according to any one of claims 1 to 4, wherein
the first cooling passage (21;44) has a shorter length than the second cooling passage (22;45) and, at the upstream end portion (16) of the segment body (11;41;51) in the axial direction of the ring segment (10;40;50), is disposed further to the outer circumferential surface side of the main body (12;42) of the segment body (11;41;51) than the second cooling passage (22). - The ring segment (10) according to any one of claims 1 to 5, wherein
the hole diameter of the second cooling passage (22) is smaller than the hole diameter of the first cooling passage (21). - The ring segment (10) according to any one of claims 1 to 6, wherein
the hole pitch of the second cooling passage (22) in the circumferential direction of the ring segment (10) is smaller than the hole pitch of the first cooling passage (21) in the circumferential direction of the ring segment (10). - The ring segment (10;50) according to any one of claims 1 to 4, further comprising:a third cooling passage (25) that is arranged at a side end portion (18) on the upstream of the segment body (11) in the circumferential direction of the ring segment (10;50) with respect to the rotation direction (R) of the rotating shaft (5), and that allows communication from the cooling space (29) to the combustion gas space (W) in the side end portion (18).
- The ring segment (10;50) according to any one of claims 1 to 4 and claim 8, further comprising:a fourth cooling passage (27) that is arranged at a side end portion (19) on the downstream of the segment body (11) in the circumferential direction of the ring segment (10;50) with respect to the rotation direction (R) of the rotating shaft (5), and that allows communication from the cooling space (29) to the combustion gas space (W) in the side end portion (19).
- The ring segment (50) according to claim 8 or claim 9, wherein
the third cooling passage (25) or the fourth cooling passage (27) communicates with the first cavity (20) via a second cavity (24) or a third cavity (26). - A gas turbine (1) provided with a ring segment (10;40;50) according to any one of claims 1 to 10 such that the circumferential direction of the ring segment (10;40;50) corresponds to a rotation direction (R) of a rotating shaft (5) and an axial direction of the rotating shaft (5) is parallel to a flow direction of a combustion gas (FG) through the gas turbine (1) during operation and the axial direction of the ring segment (10; 40; 50).
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US23631009P | 2009-08-24 | 2009-08-24 | |
EP09848691.3A EP2405103B1 (en) | 2009-08-24 | 2009-09-29 | Split ring cooling structure |
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EP09848691.3A Division EP2405103B1 (en) | 2009-08-24 | 2009-09-29 | Split ring cooling structure |
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JP (1) | JP5291799B2 (en) |
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Families Citing this family (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8894352B2 (en) * | 2010-09-07 | 2014-11-25 | Siemens Energy, Inc. | Ring segment with forked cooling passages |
EP2574732A2 (en) * | 2011-09-29 | 2013-04-03 | Hitachi Ltd. | Gas turbine |
US9017012B2 (en) * | 2011-10-26 | 2015-04-28 | Siemens Energy, Inc. | Ring segment with cooling fluid supply trench |
US9127549B2 (en) * | 2012-04-26 | 2015-09-08 | General Electric Company | Turbine shroud cooling assembly for a gas turbine system |
CN103133063A (en) * | 2013-03-01 | 2013-06-05 | 哈尔滨汽轮机厂有限责任公司 | First-stage moving vane protection ring cooling mechanism for heavy medium-low calorific value gas turbine |
JP5567180B1 (en) * | 2013-05-20 | 2014-08-06 | 川崎重工業株式会社 | Turbine blade cooling structure |
EP2835504A1 (en) * | 2013-08-09 | 2015-02-11 | Siemens Aktiengesellschaft | Insert element and gas turbine |
EP2835500A1 (en) * | 2013-08-09 | 2015-02-11 | Siemens Aktiengesellschaft | Insert element and gas turbine |
US10731858B2 (en) * | 2013-09-16 | 2020-08-04 | Raytheon Technologies Corporation | Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine |
JP6466647B2 (en) | 2014-03-27 | 2019-02-06 | 三菱日立パワーシステムズ株式会社 | Gas turbine split ring cooling structure and gas turbine having the same |
EP3183431B1 (en) | 2014-08-22 | 2018-10-10 | Siemens Aktiengesellschaft | Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines |
US9982560B2 (en) * | 2015-01-16 | 2018-05-29 | United Technologies Corporation | Cooling feed orifices |
US9784125B2 (en) | 2015-05-05 | 2017-10-10 | United Technologies Corporation | Blade outer air seals with channels |
GB201508551D0 (en) | 2015-05-19 | 2015-07-01 | Rolls Royce Plc | A heat exchanger for a gas turbine engine |
EP3118420A1 (en) * | 2015-07-15 | 2017-01-18 | Siemens Aktiengesellschaft | Coolable wall element with impingement plate |
JP6725273B2 (en) * | 2016-03-11 | 2020-07-15 | 三菱日立パワーシステムズ株式会社 | Wing, gas turbine equipped with this |
GB201612646D0 (en) * | 2016-07-21 | 2016-09-07 | Rolls Royce Plc | An air cooled component for a gas turbine engine |
JP6746486B2 (en) * | 2016-12-14 | 2020-08-26 | 三菱日立パワーシステムズ株式会社 | Split ring and gas turbine |
FR3061738B1 (en) * | 2017-01-12 | 2019-05-31 | Safran Aircraft Engines | TURBINE RING ASSEMBLY |
KR101913122B1 (en) * | 2017-02-06 | 2018-10-31 | 두산중공업 주식회사 | Gas Turbine Ring Segment Having Cooling Hole With Serial Structure, And Gas Turbine Having The Same |
KR101901683B1 (en) * | 2017-02-06 | 2018-09-27 | 두산중공업 주식회사 | Gas Turbine Ring Segment Having Straight Type Cooling Hole, And Gas Turbine Having The Same |
JP6925862B2 (en) * | 2017-05-16 | 2021-08-25 | 三菱パワー株式会社 | Manufacturing method of gas turbine and blade ring |
US10753232B2 (en) * | 2017-06-16 | 2020-08-25 | General Electric Company | Assemblies and methods for cooling flowpath support structure and flowpath components |
KR20190033255A (en) | 2017-09-21 | 2019-03-29 | 두산중공업 주식회사 | Gas turbine |
CN109538305A (en) * | 2018-11-23 | 2019-03-29 | 东方电气集团东方汽轮机有限公司 | A kind of gas turbine segmentation ring cooling structure |
JP7234006B2 (en) | 2019-03-29 | 2023-03-07 | 三菱重工業株式会社 | High temperature parts and method for manufacturing high temperature parts |
KR102226741B1 (en) * | 2019-06-25 | 2021-03-12 | 두산중공업 주식회사 | Ring segment, and turbine including the same |
US11098612B2 (en) * | 2019-11-18 | 2021-08-24 | Raytheon Technologies Corporation | Blade outer air seal including cooling trench |
KR102291801B1 (en) | 2020-02-11 | 2021-08-24 | 두산중공업 주식회사 | Ring segment and gas turbine including the same |
JP7390920B2 (en) * | 2020-02-14 | 2023-12-04 | 三菱重工業株式会社 | Boosting equipment, carbon dioxide cycle plants and combined cycle plants |
JP6799702B1 (en) | 2020-03-19 | 2020-12-16 | 三菱パワー株式会社 | Static blade and gas turbine |
JP7356397B2 (en) * | 2020-04-17 | 2023-10-04 | 三菱重工業株式会社 | High temperature parts and rotating machinery |
US11365645B2 (en) * | 2020-10-07 | 2022-06-21 | Pratt & Whitney Canada Corp. | Turbine shroud cooling |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4435322B4 (en) * | 1994-10-01 | 2005-05-04 | Alstom | Method and device for shaft seal and for cooling on the exhaust side of an axial flowed gas turbine |
US5584651A (en) * | 1994-10-31 | 1996-12-17 | General Electric Company | Cooled shroud |
DE19651881A1 (en) * | 1996-12-13 | 1998-06-18 | Asea Brown Boveri | Combustion chamber with integrated guide vanes |
JP2961091B2 (en) * | 1997-07-08 | 1999-10-12 | 三菱重工業株式会社 | Gas turbine split ring cooling hole structure |
JP3999395B2 (en) | 1999-03-03 | 2007-10-31 | 三菱重工業株式会社 | Gas turbine split ring |
US6508623B1 (en) * | 2000-03-07 | 2003-01-21 | Mitsubishi Heavy Industries, Ltd. | Gas turbine segmental ring |
GB0117110D0 (en) * | 2001-07-13 | 2001-09-05 | Siemens Ag | Coolable segment for a turbomachinery and combustion turbine |
US7033138B2 (en) * | 2002-09-06 | 2006-04-25 | Mitsubishi Heavy Industries, Ltd. | Ring segment of gas turbine |
US6758651B2 (en) * | 2002-10-16 | 2004-07-06 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
US6899518B2 (en) * | 2002-12-23 | 2005-05-31 | Pratt & Whitney Canada Corp. | Turbine shroud segment apparatus for reusing cooling air |
FR2857406B1 (en) * | 2003-07-10 | 2005-09-30 | Snecma Moteurs | COOLING THE TURBINE RINGS |
US7520715B2 (en) * | 2005-07-19 | 2009-04-21 | Pratt & Whitney Canada Corp. | Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavities |
CA2644099C (en) * | 2006-03-02 | 2013-12-31 | Ihi Corporation | Impingement cooled structure |
-
2009
- 2009-09-29 CN CN201410174274.2A patent/CN103925015B/en active Active
- 2009-09-29 CN CN200980158960.8A patent/CN102414398B/en active Active
- 2009-09-29 KR KR1020117025365A patent/KR101366908B1/en active IP Right Grant
- 2009-09-29 WO PCT/JP2009/004990 patent/WO2011024242A1/en active Application Filing
- 2009-09-29 EP EP15188702.3A patent/EP3006678B1/en active Active
- 2009-09-29 EP EP09848691.3A patent/EP2405103B1/en active Active
- 2009-09-29 JP JP2011528529A patent/JP5291799B2/en active Active
-
2010
- 2010-08-23 US US12/861,339 patent/US8777559B2/en active Active
-
2014
- 2014-04-29 US US14/264,552 patent/US9540947B2/en active Active
Non-Patent Citations (1)
Title |
---|
None * |
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CN102414398B (en) | 2014-10-29 |
CN103925015B (en) | 2016-01-20 |
EP2405103B1 (en) | 2016-05-04 |
JPWO2011024242A1 (en) | 2013-01-24 |
US9540947B2 (en) | 2017-01-10 |
US20110044805A1 (en) | 2011-02-24 |
EP3006678A1 (en) | 2016-04-13 |
WO2011024242A1 (en) | 2011-03-03 |
KR20120018753A (en) | 2012-03-05 |
CN103925015A (en) | 2014-07-16 |
EP2405103A1 (en) | 2012-01-11 |
JP5291799B2 (en) | 2013-09-18 |
EP2405103A4 (en) | 2015-02-25 |
US8777559B2 (en) | 2014-07-15 |
US20140234077A1 (en) | 2014-08-21 |
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